The invention relates to an axial flow machine, in particular a gas turbine with axial hot gas flow. Gaps between rotor-side heat shields are blocked by easily mountable sealing strips, which are arranged with their longitudinal edges in opposing grooves in the side walls of the respective gap.

A bladed rotor wheel for a turbine engine, the rotor wheel including a disk including, formed in its outer periphery, at least one slot for mounting the roots of blades, and a spacer mounted between each blade root and a bottom of the slot. The spacer includes at least one member of type that is bistable in position and that can occupy a first stable position for assembly or disassembly in which the member does not exert force on the blade root, and a second stable position in which the bistable member exerts a radial force on the blade root. The spacer also includes at least one resilient damper member mounted between the bottom of the slot and the blade root.

A turbine engine has a rotatable disk, a seal cartridge, and a blade. The rotatable disk has a peripheral surface, with at least one slot located in the peripheral surface. The seal cartridge defines a blade seat. The blade has a root, a leading edge and a trailing edge, the root being received within the blade seat.

Proposed is a turbine blade seal assembly structure including a turbine blade comprising an airfoil part, a platform part, and a root part, a turbine rotor disk allowing the root part of the turbine blade to be mounted thereto and having a mounting rib extending radially from one axial side of the turbine rotor disk to form a mounting groove, a retainer plate mounted between the platform part and one side part of the turbine rotor disk so as to seal a cooling flow path formed inside the root part and the platform part, and an insert key inserted axially into an upper end of the mounting rib and inserted into a lower end of the retainer plate to support the retainer plate.

A turbine engine has a rotatable disk, a seal cartridge, and a blade. The rotatable disk has a peripheral surface, with at least one slot located in the peripheral surface. The seal cartridge defines a blade seat. The blade has a root, a leading edge and a trailing edge, the root being received within the blade seat.

A turbine rotor of a turbine engine of an aircraft, the rotor comprising a rotor disc provided at its periphery with a plurality of cavities for receiving the root of a blade. Each blade includes a circumferential coupling rib, a plurality of platforms, a main wall that is extended at its two ends by an upstream radial wall and by a downstream radial wall, the two longitudinal edges of each platform comprising a groove for receiving part of said coupling rib of one of the two blades between which this platform is assembled, and in that the height of each upstream radial wall is such that said wall extends radially inwards beyond the bottom of the cavity, until it is in front of the upstream face of the rotor disc.

A device for axially retaining a moving blade of a low-pressure turbine in a recess of a rotor disc of axis of the turbine. This device includes a stop part intended to extend between an upstream face of a blade root of the moving blade and a downstream face of the root of the moving blade, the stop part including a first wall which forms an end stop for the upstream face of the blade root, a second wall which forms an end stop for the downstream face of the blade root, and a connection surface intended to extend between the first and the second wall along a radially inner end face of the blade root.

A fan includes a rotor hub comprising a slot and a blade comprising an airfoil extending from a blade root in a first direction. The blade root is configured to be received in the slot. The fan also includes a deformable spacer situated between the rotor hub and the blade root in the slot, a first blade lock situated at a first side of the slot, and a second blade lock situated at a second side of the slot opposite the first side. At least one of the first and second blade locks includes a tab configured to extend between the blade root and the rotor hub and to compress the spacer such that the spacer exerts a force on the blade in the first direction. A method of assembling a fan and another example fan are also disclosed.

A masking system for selectively masking a component includes a first piece, a second piece, and a third piece. The first piece has a groove. The second piece has a projection, a first channel, and a second channel. The third piece has a first wall, a second wall, a first sidewall, and a second sidewall. The first sidewall has a first notch. The groove is configured to receive the projection to connect the first piece and the second piece. The second wall of the third piece is configured to be insertably received by the first channel and the second channel such that a portion of the component is accessible via the first notch.

A foil for a rotating blade of a turbomachine, configured to be mounted to a blade root of the rotating blade and including an overall U-shaped cross-section formed by two lateral legs connected through a lower surface, the lower surface covering a lower face of the blade root, the lateral legs each covering at least part of two lateral flanks of the blade root; and a blocking system for prohibiting at least some of relative movements between the blade root and the foil, the blocking system including at least one oblique tab, partially cut out of a lower surface of the foil and forming, with respect to the lower surface of the foil, a tilted plane protrusion able to be inserted into a housing formed in a lower face of the blade root.